EP1817124B1 - Element de structure file monolithique et bi-fonctionnel - Google Patents

Element de structure file monolithique et bi-fonctionnel Download PDF

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Publication number
EP1817124B1
EP1817124B1 EP05814985A EP05814985A EP1817124B1 EP 1817124 B1 EP1817124 B1 EP 1817124B1 EP 05814985 A EP05814985 A EP 05814985A EP 05814985 A EP05814985 A EP 05814985A EP 1817124 B1 EP1817124 B1 EP 1817124B1
Authority
EP
European Patent Office
Prior art keywords
alloy
structural element
alloys
aluminium
spun
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Not-in-force
Application number
EP05814985A
Other languages
German (de)
English (en)
French (fr)
Other versions
EP1817124A1 (fr
Inventor
Frank Eberl
Joël MAUSSION
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Constellium Issoire SAS
Original Assignee
Constellium France SAS
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Constellium France SAS filed Critical Constellium France SAS
Publication of EP1817124A1 publication Critical patent/EP1817124A1/fr
Application granted granted Critical
Publication of EP1817124B1 publication Critical patent/EP1817124B1/fr
Not-in-force legal-status Critical Current
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Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B21—MECHANICAL METAL-WORKING WITHOUT ESSENTIALLY REMOVING MATERIAL; PUNCHING METAL
    • B21C—MANUFACTURE OF METAL SHEETS, WIRE, RODS, TUBES OR PROFILES, OTHERWISE THAN BY ROLLING; AUXILIARY OPERATIONS USED IN CONNECTION WITH METAL-WORKING WITHOUT ESSENTIALLY REMOVING MATERIAL
    • B21C23/00—Extruding metal; Impact extrusion
    • B21C23/02—Making uncoated products
    • B21C23/04—Making uncoated products by direct extrusion
    • B21C23/08—Making wire, bars, tubes
    • B21C23/10—Making finned tubes
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B21—MECHANICAL METAL-WORKING WITHOUT ESSENTIALLY REMOVING MATERIAL; PUNCHING METAL
    • B21C—MANUFACTURE OF METAL SHEETS, WIRE, RODS, TUBES OR PROFILES, OTHERWISE THAN BY ROLLING; AUXILIARY OPERATIONS USED IN CONNECTION WITH METAL-WORKING WITHOUT ESSENTIALLY REMOVING MATERIAL
    • B21C23/00—Extruding metal; Impact extrusion
    • B21C23/01—Extruding metal; Impact extrusion starting from material of particular form or shape, e.g. mechanically pre-treated
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B21—MECHANICAL METAL-WORKING WITHOUT ESSENTIALLY REMOVING MATERIAL; PUNCHING METAL
    • B21C—MANUFACTURE OF METAL SHEETS, WIRE, RODS, TUBES OR PROFILES, OTHERWISE THAN BY ROLLING; AUXILIARY OPERATIONS USED IN CONNECTION WITH METAL-WORKING WITHOUT ESSENTIALLY REMOVING MATERIAL
    • B21C23/00—Extruding metal; Impact extrusion
    • B21C23/22—Making metal-coated products; Making products from two or more metals
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
    • B23K—SOLDERING OR UNSOLDERING; WELDING; CLADDING OR PLATING BY SOLDERING OR WELDING; CUTTING BY APPLYING HEAT LOCALLY, e.g. FLAME CUTTING; WORKING BY LASER BEAM
    • B23K20/00—Non-electric welding by applying impact or other pressure, with or without the application of heat, e.g. cladding or plating
    • B23K20/001—Non-electric welding by applying impact or other pressure, with or without the application of heat, e.g. cladding or plating by extrusion or drawing
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C1/00—Fuselages; Constructional features common to fuselages, wings, stabilising surfaces or the like
    • B64C1/06—Frames; Stringers; Longerons ; Fuselage sections
    • B64C1/12—Construction or attachment of skin panels
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T428/00—Stock material or miscellaneous articles
    • Y10T428/12—All metal or with adjacent metals
    • Y10T428/12493—Composite; i.e., plural, adjacent, spatially distinct metal components [e.g., layers, joint, etc.]
    • Y10T428/12736—Al-base component
    • Y10T428/12764—Next to Al-base component

Definitions

  • the invention relates to a new manufacturing method for bi-functional aluminum alloy spun structural elements (see for example EP-A-0 508 434 on which the preamble of the independent claims is based), as well as structural elements developed by this method.
  • the invention is particularly useful for the manufacture of weldable stiffeners for aircraft construction.
  • the problem that the present invention seeks to solve is therefore to allow the production of monolithic and bi-functional structural elements involving two different aluminum alloys, and more specifically to make possible the assembly by welding between a structural element of fusion-weldable heat-treated aluminum alloy (such as fuselage skin made of AA6056 alloy sheet metal) and a structural heat-treated aluminum alloy member known to be non-fusion weldable (such as a spun stiffener alloy AA7349).
  • a structural element of fusion-weldable heat-treated aluminum alloy such as fuselage skin made of AA6056 alloy sheet metal
  • a structural heat-treated aluminum alloy member known to be non-fusion weldable such as a spun stiffener alloy AA7349.
  • the static mechanical characteristics ie the breaking strength R m , the yield stress R p0,2 , and the elongation at break A, are determined by a tensile test according to EN 10002-1, the location and direction of sample collection being defined in EN 755-1.
  • machining includes any material removal process such as turning, milling, drilling, reaming, tapping, EDM, grinding, polishing.
  • spunbond includes tubular products and in particular spun and drawn tubes.
  • structural element or “structural element” of a mechanical construction a mechanical part whose failure is likely to endanger the safety of said construction, its users, its users or others.
  • these structural elements include the elements that make up the fuselage (such as fuselage skin (fuselage skin in English), stiffeners or stringers, bulkheads, fuselage (circumferential frames)), the wings (such as the wing skin), the stiffeners (stringers or stiffeners), the ribs (ribs) and spars (spars) and the empennage composed in particular of horizontal and vertical stabilizers horizontal or vertical stabilizers, as well as floor beams, seat tracks and doors.
  • fuselage such as fuselage skin (fuselage skin in English
  • stiffeners or stringers such as the wing skin
  • the stiffeners stringers or stiffeners
  • ribs ribs
  • spars spars
  • empennage composed in particular of horizontal and vertical stabilizers horizontal or vertical stabilizers, as well as floor beams, seat tracks and doors.
  • monolithic structural element refers here to a structural element that has been obtained, most often by machining, from a single piece of rolled, molded, forged or molded semi-finished product, without assembly, such as than riveting, welding, gluing, with another piece.
  • bi-functional structural element here refers primarily to the functions conferred by the metallurgical characteristics of the product and not by its geometrical form.
  • a spun structure element (F) comprising two coextruded alloys, in which the foot, that is to say the part intended to be fixed on the surface of another structural element (E), to form a structural element (G), is of alloy (B), and for example in the same alloy as that on which it must be fixed, while the body, which constitutes the remainder of said spun structure element (F) may be of alloy with high mechanical characteristics (A).
  • the alloy (B) may be a heat treated alloy.
  • the alloy (A) may advantageously be a heat-treated alloy, so that the structural element (G) formed by assembly between the structural elements (F) and (E) can be used in aircraft construction.
  • Such a spun structure element (F) according to the invention is therefore bifunctional, in the sense that its body meets metallurgical requirements significantly different from those of its foot.
  • the alloy (B) is a weldable alloy, especially weldable by fusion, so that the assembly between the spun structure element (F) according to the invention and the structural element (E ) can be done by welding.
  • the alloy (B) can be an alloy of the 6xxx, 5xxx or 4xxx series.
  • the alloy (A) does not need to be weldable, but that is not excluded.
  • the present invention is applicable to any combination of spinnable aluminum-based alloys.
  • the alloy (A) is an alloy of the 7xxx series, and preferably selected from the group consisting of 7049, 7149, 7249, 7349, 7449, 7050, 7055, 7075, 7036, 7068 alloys.
  • 7136 and the alloy (B) is selected from the group consisting of 4xxx, 5xxx, 6xxx, and preferably 6056, 6056A, 6156, 6013, 6060, 6110, 5005, 5083, 5086 fusion-weldable alloys. It is also possible to use other Al-Zn-Cu-Mg alloys for the alloy (A), and especially those with a high zinc content (> 8.7%).
  • an alloy (B) which can be welded by friction stir welding.
  • This also provides a bi-functional spun structure element (F).
  • the alloy (A) can be selected from the group consisting of alloys 7049, 7149, 7249, 7349, 7449, 7050, 7055, 7075, 7068, 7036
  • the alloy (B) can be an alloy of the 2xxx series, and may be selected from the group consisting of alloys 2024, 2024A, 2056, 2124, 2224, 2324, 2424, 2524.
  • the assembly of the structural elements (F ) and (E) is not necessarily done by welding, but can be done by traditional methods of riveting.
  • This type of bi-functional structural elements can also find direct applications, ie which do not involve an assembly with other structural elements.
  • an axially symmetrical composite hollow billet is first produced, which concentrically comprises two circular section tubes, the inner alloy tube (B) of outside diameter D being threaded into the alloy outer tube ( A) of inner diameter D.
  • This insertion can be made by hot expansion of the outer tube. It is however preferred to operate by cold contraction of the inner tube; the Applicant has found that the use of this latter method of insertion leads to the spun structural element (F) at a force larger tear.
  • the Applicant has found that it is very important that in the composite hollow billet, the difference in axial symmetry is as small as possible, since it has a direct effect on the symmetry of the section of the spun hollow tube, and especially on the consistency of the thickness of the inner wall as well as the penetration height (defined on the figure 6 ) of the alloy (B) in the body of the structural element (F).
  • the cutting in step (c) can be performed according to known techniques. This is a longitudinal cut to obtain long segments of the spun structure element, which can be cut to the desired length.
  • the fins of the spun hollow tube become the body of the structural element (F), while the hollow tube itself becomes its foot. It may be advantageous to complete the foot by machining.
  • a monolithic and bifunctional structural element (F) is thus obtained, the body of which has, for example, particularly high static mechanical strength characteristics, whereas the foot has, for example, a particularly high resistance to fatigue, or the characteristic technique to be weldable by fusion.
  • the spun structure element (F) according to the invention may also be manufactured by any other method which provides a sufficiently strong metallurgical bond between the foot and the body, as characterized by the pulling force of the body.
  • the method described above based on needle spinning of an axially symmetrical composite hollow billet, gives better results than the use of a billet assembled sequentially from two billets of equal outside diameter ( figure 3 ). When using such a billet according to the figure 3 it is not done by needle spinning. It is also possible to use, instead of a cast billet, a concentric tube consisting of two spun and possibly machined tubes.
  • the advantage of using an axially symmetrical composite hollow billet is that this method ensures a good homogeneity of the spun product, and in particular a fairly constant distribution of the two alloys on the foot and the body of the spun structural element (F). depending on the length of the spun hollow tube.
  • the inventors have observed that between the beginning and the end of the hollow tube spun from a composite hollow billet with axial symmetry, the height h (defined on the figure 6 ) decreases from about 6 mm to about 3 mm. This slight inhomogeneity does not seem to have an appreciable negative effect on the properties of use of the structural element (F).
  • the inventors have found that the use of a reverse spinning process of an axially symmetric composite hollow billet as described above minimizes this inhomogeneity.
  • the method according to the invention makes it possible to manufacture structural elements (G) by welding the spun structure element (F) with another structural element (E), in which the application of a tearing force to the body of the structural element (F) does not normally lead to a break between the foot and the body. This means that we do not observe a mechanical fragility of the interface between the alloys (A) and (B).
  • Such a welded structure element (G) may be a fuselage element of an aircraft.
  • the figure 8 shows a fuselage panel (10), representing the product (E), of which one of the surfaces (11) has been machined.
  • a spun structure element (F) according to the invention (reference numeral 12), with a weldable alloy foot (13) and a body (14), was welded to the product (E), with the formation of a welded zone (15).
  • any eventual heat treatment is done on the welded part.
  • heat treatments of income can add up. Therefore, it is necessary that the state of heat treatment of the structural elements (F) and (E) is well chosen to arrive through a heat treatment after welding to a final state of the structural element (G) which is satisfactory, for example by the through pre-income on one or the other element.
  • a 7xxx alloy stiffener requires a revenue of a shorter total duration than a half-product 6xxx alloy.
  • the 6xxx alloy sheets must have been pre-tempered before welding, since the duration of the heat treatment they can undergo after welding is limited by the shorter duration of the treatment of income that the 7xxx alloy stiffeners must undergo after welding.
  • the body of the extruded structure element (F), which is made of alloy (A) and which is fixed, for example by welding or riveting, to a product or structural element ( E), can be fixed, for example by riveting or bolting, on other products.
  • This embodiment is illustrated on the figure 10 which shows a product (20), representing the product (E), of which one of the surfaces (11) has been machined.
  • a spun structure element (F) according to the invention (reference numeral 12), with a weldable alloy foot (13) and a body (14), was welded to the product (E), with the formation of a welded zone (15).
  • the body (14) of the spun structure member is rivet (16) attached to another structural member (17).
  • a complex structural element can be used in aeronautical construction as a fuselage frame assembly: in this case the body (14) of the bi-functional spun section (F) according to the invention (12) is made of alloy the 2xxx series, and the foot (13) in 4xxx, 5xxx or 7xxx alloy, the product (20) is the fuselage skin, (12) is a "stiffener" (in English shear web), and (17) the frame .
  • the figure 9 shows an embodiment of a structural element (G) from a bi-functional spun structure element (F) according to the invention by riveting.
  • the bifunctional structural member (12) has a high strength 7xxx series alloy body (14) and a high damage tolerance foot (13) of the 2xxx series alloy.
  • the foot (13) is fixed by rivets (16) on two adjacent structural elements (E) (item 18).
  • Such a structural element (G) can be used for the construction of the aircraft fuselage.
  • spun structural elements are manufactured with an AA7349 alloy body and an alloy foot AA6056 (reference P6) or alloy AA5086 (reference P5).
  • a hollow spinning billet having an outer concentric portion made of AA7349 alloy and a concentric inner portion of AA6056 or AA5086 alloy is prepared in the following manner: a first billet of AA7349 alloy is cast and a cylinder with an outside diameter of 189 mm. In this cylinder, there is arranged a circular section of channel (diameter D) so that the longitudinal axis of the cylinder and the longitudinal axis of the channel coincide. Said channel traverses the entire length of said cylinder.
  • a cylinder with an outer diameter D and a circular section of channel (diameter d) is prepared so that the longitudinal axis of the cylinder and the longitudinal axis of the channel coincide. Said channel traverses the entire length of said cylinder.
  • the alloy tube 6056 is inserted into the alloy tube 7349.
  • a hollow cylindrical billet is thus obtained, the section of which is shown schematically in FIG. figure 1 . It is spun on needle by direct spinning at a block temperature of 420 ° C. The section of the extruded profile is shown on the figure 2 . In this example, the extrusion ratio is 11.
  • the profile obtained was cut in the direction of its length: a length of profile thus gives eight lengths of stiffener (see figure 2 ).
  • the quality of the metallurgical bond between the two alloys (A) and (B) is characterized by measuring the tearing force of the body of the structural element when the foot is fixed in a rigid holding device.
  • This device is shown schematically on the figure 7 .
  • a section of the structural element (F) to be tested is cut out and fixed between jaws 1, 2.
  • the shape of the jaws is adapted to the curvature of the product to guarantee perfect contact between the jaws and the sample. .
  • the body 3 of the product is caught between the jaws (not shown in FIG. figure 7 ) a traction machine.
  • a pulling force 4 is applied and increased until the product to be tested breaks. We record the force.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Pressure Welding/Diffusion-Bonding (AREA)
  • Extrusion Of Metal (AREA)
  • Manufacture Of Alloys Or Alloy Compounds (AREA)
  • Floor Finish (AREA)
EP05814985A 2004-10-27 2005-10-26 Element de structure file monolithique et bi-fonctionnel Not-in-force EP1817124B1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR0411442A FR2876924B1 (fr) 2004-10-27 2004-10-27 Element de structure file monolithique et bi-fonctionnel
PCT/FR2005/002669 WO2006045952A1 (fr) 2004-10-27 2005-10-26 Element de structure file monolithique et bi-fonctionnel

Publications (2)

Publication Number Publication Date
EP1817124A1 EP1817124A1 (fr) 2007-08-15
EP1817124B1 true EP1817124B1 (fr) 2012-12-05

Family

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Family Applications (1)

Application Number Title Priority Date Filing Date
EP05814985A Not-in-force EP1817124B1 (fr) 2004-10-27 2005-10-26 Element de structure file monolithique et bi-fonctionnel

Country Status (10)

Country Link
US (1) US7862903B2 (es)
EP (1) EP1817124B1 (es)
JP (1) JP2008517829A (es)
CN (1) CN101048240B (es)
BR (1) BRPI0517400B1 (es)
CA (1) CA2581378C (es)
ES (1) ES2400573T3 (es)
FR (1) FR2876924B1 (es)
UA (1) UA90284C2 (es)
WO (1) WO2006045952A1 (es)

Families Citing this family (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2006030123A2 (fr) * 2004-09-14 2006-03-23 Alcan Rhenalu Element de structure soude comprenant au moins deux parties en alliages d'aluminium differents ou presentants un etat metallurgique different, procede de fabrication d'un tel element
EP1965935A1 (en) * 2005-11-09 2008-09-10 Alcoa Inc. A multi-alloy monolithic extruded structural member and method of producing thereof
TW200824810A (en) * 2006-12-13 2008-06-16 Hwan Chee Metal Co Ltd Process for fabricating extruded parts made of aluminum composite materials and extruded parts made by same
DE102007038713B4 (de) * 2007-08-14 2009-07-23 Thyssenkrupp Steel Ag Verfahren zur Herstellung von partiell verstärkten Hohlprofilen
DE102009032435B4 (de) * 2009-07-09 2012-08-16 Fraunhofer-Gesellschaft zur Förderung der angewandten Forschung e.V. Verfahren und Vorrichtung zur Herstellung eines querfließgepressten Verbundkörpers und querfließgepresster Verbundkörper
CA3032261A1 (en) 2016-08-26 2018-03-01 Shape Corp. Warm forming process and apparatus for transverse bending of an extruded aluminum beam to warm form a vehicle structural component
EP3529394A4 (en) 2016-10-24 2020-06-24 Shape Corp. MULTI-STAGE MOLDING OF ALUMINUM ALLOYS AND THERMAL TREATMENT METHOD FOR PRODUCING VEHICLE COMPONENTS

Citations (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2007070731A1 (en) * 2005-11-09 2007-06-21 Alcoa Inc. A multi-alloy monolithic extruded structural member and method of producing thereof

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US2798604A (en) * 1956-04-20 1957-07-09 Aluminum Co Of America Extrusion
US3482003A (en) * 1967-12-06 1969-12-02 Atomic Energy Commission Method of extrusion of ribbed composite members
JPS5461015A (en) * 1977-10-25 1979-05-17 Kobe Steel Ltd Manufacture of aluminum-soldered fin heat exchanger
ZA82703B (en) * 1981-02-18 1982-12-29 Babcock & Wilcox Co Method of preparing multimetal extrusion billets
DE4111509A1 (de) * 1991-04-09 1992-10-15 Austria Metall Verfahren zum herstellen von strangpressprofilteilen
DE19639667C1 (de) * 1996-09-27 1998-03-12 Daimler Benz Aerospace Airbus Verfahren zum Schweißen von Profilen auf großformatigen Aluminium-Strukturbauteilen mittels Laserstrahlen
DE19739595C1 (de) * 1997-09-10 1999-02-04 Daimler Benz Ag Profil für einen Kipperboden
US6712315B2 (en) * 2000-11-30 2004-03-30 Airbus Deutschland Gmbh Metal structural component for an aircraft, with resistance to crack propagation
JP2003277898A (ja) * 2002-03-27 2003-10-02 Society Of Japanese Aerospace Co Inc 航空機用ストリンガー
US7360676B2 (en) * 2002-09-21 2008-04-22 Universal Alloy Corporation Welded aluminum alloy structure

Patent Citations (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2007070731A1 (en) * 2005-11-09 2007-06-21 Alcoa Inc. A multi-alloy monolithic extruded structural member and method of producing thereof

Also Published As

Publication number Publication date
CA2581378A1 (fr) 2006-05-04
EP1817124A1 (fr) 2007-08-15
ES2400573T3 (es) 2013-04-10
BRPI0517400A (pt) 2008-10-14
US20060118213A1 (en) 2006-06-08
BRPI0517400B1 (pt) 2019-03-26
CA2581378C (fr) 2013-02-19
BRPI0517400A8 (pt) 2016-11-08
JP2008517829A (ja) 2008-05-29
UA90284C2 (ru) 2010-04-26
US7862903B2 (en) 2011-01-04
CN101048240B (zh) 2010-12-08
CN101048240A (zh) 2007-10-03
WO2006045952A1 (fr) 2006-05-04
FR2876924A1 (fr) 2006-04-28
FR2876924B1 (fr) 2006-12-08

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